Vent system for use in a gas turbine and method of operating thereof

ABSTRACT

A vent for use in a gaseous fuel supply circuit of a gas turbine is provided. The vent includes an inlet in flow communication with the gaseous fuel supply circuit, a first outlet in flow communication with the gaseous fuel supply circuit and configured to release gaseous fuel at atmospheric pressure, a first valve coupled between the inlet and the first outlet, wherein the first valve includes a second outlet configured to channel the gaseous fuel towards a combustion device. The system also includes a second valve coupled between the inlet and the second outlet, and a control device configured to selectively open and close the first and second valves based on a pressure of the gaseous fuel.

This invention concerns gas turbines and more particularly evacuation devices, or vents for gaseous fuel powering the gas turbines.

The gas turbines are powered by a gaseous fuel routed through a supply circuit. The gaseous fuel supply circuit must regulate the flow and pressure of gaseous fuel which powers the gas turbine, as well as ensure rapid security of the circuit. For this, the supply circuit comprises of several valves fitted in series on the gaseous fuel routing pipes.

In case of emergency shutdown of the system, for example, in case of detection of gas leakage or excess speed of the gas turbine, the gaseous fuel supply circuit must be drained within a very short period, preferably within 30 seconds, to obtain a residual pressure in the close circuit of the atmospheric pressure. Then, it is known to release the residual gaseous fuel in the supply circuit in the atmosphere.

Furthermore, while starting the gas turbine, it is also necessary to supply the turbine with a gaseous fuel having a temperature greater than a determined value, to obtain the conditions required in the combustion chamber to be able to start the turbine. For this purpose, the supply circuit comprises of one or more heating devices capable of gradually increasing the gaseous fuel temperature while being routed towards the combustion chamber. However, as long as the gaseous fuel has not reached the desired temperature, it cannot power the combustion chamber, and is generally released in the atmosphere.

However, the discharge of gaseous fuel in the atmosphere has several disadvantages, on the one hand from the environmental point of view (toxicity of gaseous fuel), and on the other hand, from the security point of view. The volume of gaseous fuel released in the atmosphere may be difficult to disperse due to the large volume released, density of gaseous fuel or topography of the site where the gaseous fuel is released.

The JP 08200650 document discloses a gaseous fuel routing device comprising of one vent to release the gaseous fuel.

Thus, the invention must resolve the problems described above. In particular, one of the aims of the invention is to propose a vent, or gaseous fuel evacuation device, which allows limiting the discharge of gaseous fuel in the atmosphere, particularly at the time of emergency shutdown or while starting a gas turbine. One aim of the invention is also to preserve the security conditions required, in terms of depressurization period of the supply circuit, maximum residual vacuum pressure in the supply circuit, reliability, . . .

According to the invention, a vent is proposed for the gaseous fuel supply circuit of a gas turbine, comprising of an inlet to be connected to the gaseous fuel supply circuit, a first outlet capable of releasing the gaseous fuel at atmospheric pressure, and a first valve fitted between the inlet and the first outlet. The vent also comprises of a second outlet capable of providing gaseous fuel through combustion at atmospheric pressure, for example, a flare, a second valve fitted between the inlet and the second outlet, and an control device capable of controlling the opening and closing of the first and second valves according to the pressure of gaseous fuel.

Thus, according to the invention, the vent provides an independent combustion device of the gas turbine, and allows burning gaseous fuel before releasing in the atmosphere. The combustion device, for example a flare, also allows releasing the residual gaseous fuel present in the gaseous fuel supply circuit, and obtaining a residual pressure almost identical to the atmospheric pressure as the combustion takes place at a pressure that is almost identical or sensitively equal to the atmospheric pressure. Finally, the combustion device can be easily dimensioned in order to obtain the combustion of a given flow of gaseous fuel, thus facilitating the limited period of purge of the supply circuit.

Furthermore, the vent also allows limiting the risks of combustion of gaseous fuel in the supply circuit, by providing an outlet towards the atmosphere, when the gaseous fuel pressure is less than a determined value. In particular, according to the invention, the vent allows preventing transfer between the outlet towards the combustion device and the outlet towards the atmosphere. Thus, it is possible to maintain the circuit in a stable and safe state, by maintaining pressure in the supply circuit at a level equal to that of the atmospheric pressure. Furthermore, the vent allows limiting the discharge of gaseous fuel in the atmosphere by opening the outlet towards the atmosphere only at the end of each drain stage of the supply circuit, when the gaseous fuel pressure is almost identical to the atmospheric pressure.

Preferably, the vent also comprises of a third valve fitted between the inlet and the second outlet and the control device is capable of controlling the opening and closing of the third valve according to the temperature of the gaseous fuel in the supply circuit. The third valve may be used specifically for the start phases: it is then controlled by the temperature of gaseous fuel, and it closes when the temperature of gaseous fuel attains the desired value. In this case, no gaseous fuel is released in the atmosphere in the start phase of the gas turbine.

Also, according to another aspect, the invention concerns a supply circuit for gas turbine comprising of a vent such as described before.

The supply circuit may also have a gaseous fuel pressure measurement device, and the control device may receive in inlet the measurements of the pressure measurement device.

The supply circuit may also comprise of an insulation valve and a regulation valve fitted downstream of the insulation valve, and the vent inlet may be fitted between the insulation valve and the regulation valve. During depressurization of a supply circuit, a considerable quantity of gas is present between the insulation valve and the regulation valve. This is why, according to the invention, the vent is preferably fitted between these two valves, in order to allow burning of a large quantity of gaseous fuel in the combustion device.

The supply circuit may also comprise of a gas control valve fitted downstream of the regulation valve and a vent towards the atmosphere fitted between the regulation valve and the gas control valve. In the part of the supply circuit located between the regulation valve and the gas control valve, the quantity of gaseous fuel present therein is relatively limited, in a manner that a vent direct to the atmosphere is possible.

The invention is also related to a gas turbine comprising of a supply circuit as described before.

As per another aspect, the invention is also related to a gaseous fuel evacuation process present in a gaseous fuel supply circuit of a gas turbine, in which:

-   -   the gaseous fuel to be evacuated is routed towards a combustion         device at atmospheric pressure, for example a flare, when the         pressure of the gaseous fuel is greater than a determined         pressure, for example, the flare usage pressure, then     -   the gaseous fuel to be evacuated is routed towards the         atmosphere until a pressure equal to the atmospheric pressure is         obtained in the gaseous fuel supply circuit.

Preferably, the gaseous fuel present in the supply circuit is evacuated towards the flare when the gas turbine is stopped urgently or when the gas turbine is in start phase and that the gaseous fuel temperature is less than a fixed temperature.

Preferably, the gas turbine comprises of an insulation valve and a regulation valve fitted downstream of the insulation valve, and the gaseous fuel evacuated when the gas turbine is shutdown urgently is the gaseous fuel contained between the insulation valve and the regulation valve.

Other advantages and features of the invention will appear on examination of the detailed description of a mode of execution of the invention which is not limited, and the designs attached, of which:

FIG. 1 represents a gas turbine in a diagram;

in a diagram, FIG. 2 illustrates a gaseous fuel supply circuit with vent according to the invention; and

FIG. 3 represents an example of the vent control model, in an emergency shutdown phase.

FIG. 1 represents, in a diagram, a gas turbine 1 powered with gaseous fuel from, for example, a tank 2. The gas turbines are generally used in the electric power plants, to drive the generators and to produce electric energy. The gas turbine 1 comprises of an axial compressor 3 with one rotor shaft 4. The air is introduced by the inlet 5 of the compressor, is compressed by the axial compressor 3 then routed towards a combustion chamber 6. The combustion chamber 6 is also powered by a gaseous fuel, for example natural gas which, during combustion, produces hot gases with high energy capable of driving a turbine 7. The gaseous fuel may be routed from the tank 2 to the combustion chamber 6 through a gaseous fuel supply circuit 8 which comprises of an inlet connected to the tank 2 and an outlet connected to the combustion chamber 6.

In turbine 7, the energy from the hot gases is converted during operation and a part of it is used to drive the compressor 3, through the rotor shaft 4, and whose other part is used to drive an electricity production generator 9, through a shaft 10. Then, the exhaust gases come out of the turbine 7 through an outlet 11, and may be used for other applications.

FIG. 2 represents in a detailed manner the gaseous fuel supply circuit 8 of the combustion chamber. The supply circuit 8 comprises of an inlet 12 to receive the gaseous fuel, and outlets 13 to provide the combustion chamber with gaseous fuel, and a routing line 14 connecting the inlet 12 with the outlets 13. The gaseous fuel routing line 14 successively comprises, in the direction of circulation of gaseous fuel: an insulation valve 15 (in English Safety Shut-Off valve SSOV) connected to the inlet 12, a regulation valve 16 (in English: Stop Ratio Valve SRV) fitted downstream of the insulation valve 15, and supply lines, for example three, fitted in parallel, downstream of the regulation valve 16 and each one comprising of a gas control valve 17 (in English: Gas Control Valve GCV) fitted upstream of an outlet 13 towards the combustion chamber.

The insulation valve 15 is a safety valve and it insulates the gaseous fuel supply circuit from the supply circuit of the combustion chamber. Thus, the valve 15 allows interrupting the gaseous fuel supply in case of gas turbine operation problem, or in case it is shutdown.

The regulation valve 16 also allows interrupting the gaseous fuel supply of the combustion chamber, but particularly allows controlling the gaseous fuel pressure in the routing line, between the regulation valve 16 and the control valves 17, which vary according to the instant speed of the turbine.

The control valves 17 determine the quantity of gaseous fuel delivered by the supply line 13 in the combustion chamber. In particular, the valves 17 may be of type sonic.

The routing line 14 may also comprise, upstream of the insulation valve 15, a heating device 18 capable of increasing the temperature of gaseous fuel before it powers the combustion chamber.

The routing line 14 also has temperature and pressure sensors. The temperature sensor 19 is fitted downstream of the heating device 18, even between the heating device 18 and the insulation valve 15, and allows knowing the temperature of gaseous fuel powering the combustion chamber. The pressure sensor 20 is fitted between the insulation valve 15 and the regulation valve 16 and allows knowing the pressure of gaseous fuel in the supply circuit 8 during operation of a gas turbine or during emergency shutdown.

According to this invention, a vent 21 is fitted on the routing line 14. More particularly, the vent 21 has a main pipe 22 tapped on the routing line 14, between the insulation valve 15 and the regulation valve 16. On the main pipe 22 is fitted a first vent valve 23 which allows releasing the gaseous fuel present in the routing line 14, between the insulation valve 15 and the regulation valve 16, in the atmosphere.

The vent 21 also has a secondary pipe 24, tapped on the main line 22, between the tap on the routing line 14 and the first vent valve 23. The secondary pipe has a second vent valve 25 towards a combustion device 26, for example a flare, an insulation valve 27 of the vent towards the flare, a parallel pipe 28 and a third vent valve 29 towards the flare.

The second vent valve 25 towards the flare, the insulation valve 27 of the vent towards the flare and the flare 26 are fitted in series on the secondary pipe 24, between the tap on the main pipe 22 and the discharge in the atmosphere. The third valve 29 of the vent towards the flare is fitted on the parallel pipe 28, and the parallel pipe 28 is fitted on the secondary pipe 24, in parallel to the second valve 25: the inlet of the parallel pipe 28 is tapped on the secondary pipe 24 upstream of the second valve 25 and the outlet of the parallel pipe 28 is tapped on the secondary pipe 24 downstream of the second valve 25 but upstream of the insulation valve of the vent 27.

The flare 26 allows burning the gaseous fuel before discharging it in the atmosphere. The insulation valve 27 allows entirely closing the secondary pipe 24 and thus insulating the flare 26 of the routing line 14, whether this is through the secondary pipe 24 or through the parallel pipe 28. The second vent valve 25 allows controlling the gaseous fuel flow circulating from the routing line 14 towards the flare 26.

Preferably, the first vent valve 23 is a valve open by default with an opening diameter of 3 inches, the second vent valve 25 is a valve closed by default with an opening diameter of 3 inches, and the third parallel valve is a valve closed by default with an opening diameter of 1 inch. The third valve 29 is preferably used in the start phases, while the second vent valve 25, which has a wider opening and thus a greater flow, is preferably used in the emergency shutdown phases, when the gaseous fuel present in the routing line 14 must be rapidly vented.

Furthermore, the supply circuit 8 may also have a secondary vent 30 towards the atmosphere. More particularly, the secondary vent 30 has a main pipe 31 tapped on the routing line 14, between the regulation valve 16 and the control valves 17. A fourth vent valve towards the atmosphere 32, which allows releasing the gaseous fuel present in the routing line 14, between the regulation valve 16 and the control valves 17, in the atmosphere, is fitted on the main pipe 31. In particular, in so far as the quantity of residual gaseous fuel found between the regulation valve 16 and the control valves 17 is much less than the quantity of residual gaseous fuel found between the insulation valve 15 and the regulation valve 16, the supply circuit 8 has only a single vent 21 towards a flare, between the insulation valve 15 and the regulation valve 16.

Thanks to the vents 21 and 30, it is now possible to evacuate the gaseous fuel found in the routing line 14, between the insulation valve 15 and the control valves 17.

Finally, the supply circuit 8 has a control device 33. The control device 33 receives the information provided by the pressure and temperature sensors 19 and 20, and is capable of controlling the different valves of the supply circuit 8 according to the mode of operation of the gas turbine.

Thus, when the gas turbine is in normal shutdown phase, the valves 16, 17, 23, 25, 27 and 29 are closed, whereas the valves 15 and 32 are opened. The valves 23, 25, 27 and 29 remain closed in order to avoid depressurization of the gaseous fuel routing line.

In the start phases, it is necessary to heat the gaseous fuel before it fills the combustion chamber. The insulation valve 15 is opened and the heating device 18 is thus used. The temperature sensor 19 allows indicating to the control device 33 if the required temperature is attained. When the temperature of the gaseous fuel is less than the required temperature, the valves 16 and 17 are closed and the gaseous fuel is vented: the valves 29 and 27 are opened in order to vent the gaseous fuel present between the valves 15 and 16 towards the flare 26, and valve 32 is opened to vent the gaseous fuel present between valve 16 and valves 17, towards the atmosphere. Valves 23 and 25 remain closed.

When the gaseous fuel attains the desired temperature, the turbine starts operating and the valves 15, 16 and 17 are opened, while the valves 23, 25, 27, 29 and 32 are closed: there is no vent and the gaseous fuel is routed towards the combustion chamber.

In case of emergency shutdown of the gas turbine, the valves 15, 16 and 17 of the routing line are all closed, and the residual gaseous fuel in the routing line must be vented. For this, valve 32 is opened to vent towards the atmosphere the gaseous fuel remaining between valve 16 and valves 17. Furthermore, the gaseous fuel present between valve 15 and valve 16 is firstly vented towards the flare: valves 25 and 27 are opened in order to allow rapid evacuation of the gaseous fuel towards the flare. Valves 23 and 29 remain closed during this period.

Then, when the pressure of the residual gaseous fuel remaining between the valves 15 and 16 and measured by the sensor 20 becomes less than a determined value, for example the supply pressure of the flare, valves 25 and 27 are closed then valve 23 is opened to finish venting the remaining residual gaseous fuel towards the atmosphere. In particular, valve 23 is opened only when after closure of valves 25 and/or 27.

FIG. 3 represents an example of the control model of valves 25 and 23 (curves (B) and (C) respectively) during and emergency shutdown phase, and variation in pressure of the gaseous fuel measured by the device 20 in the supply circuit (curve (A)). Thus, the model has a first part during which the safety valve 15 is closed. Then, in a second part, the remaining gaseous fuel is vented in the supply circuit. For this, the second valve 25 is gradually opened until it is completely open, in a manner as to feed the flare with the gaseous fuel remaining in the supply circuit: thus a rapid drop is observed in the pressure of the gaseous fuel which is burnt, on coming out, in the flare.

Then, when the pressure of the gaseous fuel in the supply circuit falls below a determined value, the second valve 25 is thus gradually closed in order to avoid transfer between the flare and the supply circuit. When the second valve 25 is completely closed, the first valve 23 may then be gradually opened, to place the routing line at atmospheric pressure, and to discharge the residual gaseous fuel in the atmosphere. Thus, a pressure equal to the atmospheric pressure is obtained in the supply circuit.

Thus, it is possible to vent the gaseous fuel contained in the supply circuit by maximizing the quantity of gaseous fuel released towards the flare while minimizing the vent period. Furthermore, the control of the vent valves according to the pressure in the supply circuit and according to the opening status of other vent valves allows safely operating the vent phase. 

1-10. (canceled)
 11. A vent system for use in a gaseous fuel supply circuit of a gas turbine, said system comprising: an inlet in flow communication with the gaseous fuel supply circuit; a first outlet in flow communication with the gaseous fuel supply circuit and configured to release gaseous fuel at atmospheric pressure; a first valve coupled between said inlet and said first outlet, said first valve comprising a second outlet configured to channel the gaseous fuel towards a combustion device; a second valve coupled between said inlet and said second outlet; and a control device configured to selectively open and close said first and second valves based on a pressure of the gaseous fuel.
 12. The system in accordance with claim 21 further comprising a third valve coupled between said inlet and said second outlet, wherein said control device is further configured to selectively open and close said third valve based on a temperature of the gaseous fuel in the supply circuit.
 13. The system in accordance with claim 22 further comprising a temperature measurement device configured to measure the temperature of the gaseous fuel, wherein said control device is configured to receive a temperature measurement from said temperature measurement device.
 14. The system in accordance with claim 21 further comprising a pressure measurement device configured to measure the pressure of the gaseous fuel, wherein said control device is configured to receive a pressure measurement from said pressure measurement device.
 15. The system in accordance with claim 21 further comprising an insulation valve and a regulation valve coupled downstream from said insulation valve, wherein said inlet is positioned between said insulation valve and said regulation valve.
 16. The system in accordance with claim 25 further comprising a fourth valve coupled downstream from said regulation valve, wherein said fourth valve is configured to release residual gaseous fuel at atmospheric pressure when said regulation valve is closed.
 17. The vent in accordance with claim 21 further comprising a gas control valve coupled downstream from said regulation valve.
 18. A gas turbine comprising: a combustor; and a gaseous fuel supply circuit coupled upstream from said combustor, said gaseous fuel supply circuit comprising a vent that comprises: an inlet in flow communication with said gaseous fuel supply circuit; a first outlet in flow communication with said gaseous fuel supply circuit and configured to release gaseous fuel at atmospheric pressure; a first valve coupled between said inlet and said first outlet, said first valve comprising a second outlet configured to channel the gaseous fuel towards a combustion device; a second valve coupled between said inlet and said second outlet; and a control device configured to selectively open and close said first and second valves based on a pressure of the gaseous fuel.
 19. The gas turbine in accordance with claim 28 further comprising a third valve coupled between said inlet and said second outlet, wherein said control device is further configured to selectively open and close said third valve based on a temperature of the gaseous fuel in the supply circuit.
 20. The gas turbine in accordance with claim 29 further comprising a temperature measurement device configured to measure the temperature of the gaseous fuel, wherein said control device is configured to receive a temperature measurement from said temperature measurement device.
 21. The gas turbine in accordance with claim 28 further comprising a pressure measurement device configured to measure the pressure of the gaseous fuel, wherein said control device is configured to receive a pressure measurement from said pressure measurement device.
 22. The gas turbine in accordance with claim 28 further comprising an insulation valve and a regulation valve coupled downstream from said insulation valve, wherein said inlet is positioned between said insulation valve and said regulation valve.
 23. The gas turbine in accordance with claim 32 further comprising a fourth valve coupled downstream from said regulation valve, wherein said fourth valve is configured to release residual gaseous fuel at atmospheric pressure when said regulation valve is closed.
 24. The gas turbine in accordance with claim 28 further comprising a gas control valve coupled downstream from said regulation valve.
 25. A method of operating a gas turbine, said method comprising: selectively channeling a flow of gaseous fuel towards a first valve and a first outlet, the first valve including a second outlet towards a combustion device the first outlet towards an atmospheric environment; coupling a second valve upstream from the first valve; and selectively opening and closing the first and second valves based on a pressure of the gaseous fuel.
 26. The method in accordance with claim 35 further comprising: coupling a third valve upstream from the first valve and in parallel with the second valve; and selectively opening and closing the third valve based on a temperature of the gaseous fuel.
 27. The method in accordance with claim 36, wherein selectively opening and closing the third valve comprises a measuring the temperature of the gaseous fuel with a temperature measurement device.
 28. The method in accordance with claim 35, wherein selectively opening and closing the first and second valves comprises measuring the pressure of the gaseous fuel with a pressure measurement device.
 29. The method in accordance with claim 35 further comprising: coupling an insulation valve upstream from the second valve; and coupling a regulation valve downstream from the insulation valve such that an inlet to the second valve is positioned between the insulation valve and the regulation valve.
 30. The method in accordance with claim 39 further comprising: coupling a fourth valve downstream from the regulation valve; and selectively opening and closing the fourth valve when the regulation valve is closed to release residual gaseous fuel to the atmospheric environment. 